CN219714752U - Aeroengine test bench with adjustable attitude angle - Google Patents
Aeroengine test bench with adjustable attitude angle Download PDFInfo
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- CN219714752U CN219714752U CN202223532220.8U CN202223532220U CN219714752U CN 219714752 U CN219714752 U CN 219714752U CN 202223532220 U CN202223532220 U CN 202223532220U CN 219714752 U CN219714752 U CN 219714752U
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Abstract
The utility model provides an aero-engine test stand with adjustable attitude angle, which relates to the technical field of aero-engine test stands, and comprises: a mounting plate; the two support frames are symmetrically arranged on the mounting plate, and the tops of the two support frames are respectively used for rotationally connecting with main mounting knots at two sides of the aero-engine; at least one first flexible subassembly, first flexible subassembly sets up between two support frames, and the one end of first flexible subassembly articulates on the mounting panel, and the other end of first flexible subassembly is used for rotating with the pair of aircraft engine tail spout top to be connected. When the attack angle or the attitude angle of the aero-engine needs to be adjusted, the aero-engine rotates by taking the main installation knot as the center of a circle through adjusting the length of the first telescopic component, the inclination angle of the aero-engine is changed, and the state of the engine in the unmanned aerial vehicle flight process is simulated so as to meet the experimental requirements.
Description
Technical Field
The utility model belongs to the technical field of aero-engine test benches, and particularly relates to an attitude angle adjustable aero-engine test bench.
Background
Before an aeroengine of a certain model unmanned aerial vehicle power system is installed, tests of relevant performance of the engine, such as durability tests, pitch matching and the like of the aeroengine, are required to be carried out, and the performance of the aeroengine can meet relevant technical requirements of the power system. Meanwhile, the engine test is an indispensable means for checking the dynamic property, economy, working reliability, wear resistance and the like of the engine, and is an indispensable important link for researching, designing and manufacturing a novel engine.
At present, the traditional test bench structure is comparatively fixed, and angle of attack, attitude angle etc. of engine can not be adjusted, can't simulate unmanned aerial vehicle flight in-process angle of attack and attitude angle's change, can not satisfy aeroengine's experimental requirement.
Disclosure of Invention
The utility model aims to provide an aeroengine test stand with adjustable attitude angle aiming at the defects of the prior art, so as to solve the problems that the traditional test stand structure provided in the prior art is relatively fixed, the attack angle, the attitude angle and the like of an engine cannot be adjusted, the change of the attack angle and the attitude angle in the flight process of an unmanned aerial vehicle cannot be simulated, and the experimental requirements of an aeroengine cannot be met.
In order to achieve the above object, the present utility model provides an attitude angle adjustable aeroengine test stand, comprising:
a mounting plate;
the two support frames are symmetrically arranged on the mounting plate, and the tops of the two support frames are respectively used for rotationally connecting with main mounting knots at two sides of the aero-engine;
the telescopic device comprises at least one first telescopic component, wherein the first telescopic component is arranged between two supporting frames, one end of the first telescopic component is hinged to the mounting plate, and the other end of the first telescopic component is used for being rotationally connected with a secondary mounting knot above a tail nozzle of an aeroengine.
Preferably, the support frame includes connecting rod and second flexible subassembly, the one end of connecting rod with the one end of second flexible subassembly is kept away from each other and all articulates on the mounting panel, the other end of connecting rod with the other end of second flexible subassembly is articulated each other and is connected.
Preferably, a round hole is formed in the other end of the connecting rod, a second shock absorber is installed in the round hole, and a center hole of the second shock absorber is used for being inserted into the corresponding main installation knot.
Preferably, the first telescopic assembly comprises:
the inner sides of two ends of the first sleeve are respectively provided with a first left-handed internal thread and a first right-handed internal thread;
the left-handed draw bar penetrates through one end of the first sleeve and is in threaded connection with the first left-handed internal thread, and the right-handed draw bar penetrates through the other end of the first sleeve and is in threaded connection with the first right-handed internal thread.
Preferably, the second telescopic assembly comprises:
the inner sides of two ends of the second sleeve are respectively provided with a second left-handed internal thread and a second right-handed internal thread;
the second left-handed pull rod penetrates through one end of the second sleeve and is in threaded connection with the second left-handed internal thread, and the second right-handed pull rod penetrates through the other end of the second sleeve and is in threaded connection with the second right-handed internal thread.
Preferably, the test bench further comprises a double-hole hinge piece and two third telescopic components, wherein the double-hole hinge piece is arranged between the two supporting frames, one end of each of the two third telescopic components is hinged to the double-hole hinge piece, and the other ends of the two third telescopic components are respectively hinged to the side walls of the two connecting rods.
Preferably, the third telescopic assembly comprises:
the inner sides of two ends of the third sleeve are respectively provided with a third left-handed internal thread and a third right-handed internal thread;
the third left-handed pull rod penetrates through one end of the third sleeve and is in threaded connection with the third left-handed internal thread, and the third right-handed pull rod penetrates through the other end of the third sleeve and is in threaded connection with the third right-handed internal thread.
Preferably, the support frame further comprises a single-hole hinge piece and a main hinge support, the single-hole hinge piece and the hinge support are far away from each other and are fixedly connected to the mounting plate, one end of the connecting rod and one end of the second telescopic component are hinged to the single-hole hinge piece and the hinge support respectively, and the center line of a hinge hole of the single-hole hinge piece is perpendicular to the center line of a hinge hole of the hinge support.
Preferably, the test bench further comprises at least one cushion block and at least one auxiliary hinged support, the cushion block is arranged between the two supporting frames, the auxiliary hinged support is fixedly connected to the cushion block, a first shock absorber is installed at one end of the first telescopic component, and the first shock absorber is hinged to the auxiliary hinged support.
Preferably, the number of the first telescopic assemblies is two, and the other ends of the two first telescopic assemblies are used for being rotationally connected with the two auxiliary mounting structures.
The utility model provides an aeroengine test bed with adjustable attitude angle, which has the beneficial effects that:
the top of two support frames of this test bench is used for respectively with the main installation knot rotation connection of aeroengine both sides, the one end of first flexible subassembly articulates on the mounting panel, the other end of first flexible subassembly is used for with the vice installation knot rotation connection of aeroengine tail spout top, when need adjust aeroengine's attack angle or attitude angle, through adjusting the length of first flexible subassembly, make aeroengine rotate with main installation knot as the centre of a circle, change aeroengine's inclination, simulate unmanned aerial vehicle flight in-process engine's state, in order to satisfy the experimental requirement.
Additional features and advantages of the utility model will be set forth in the detailed description which follows.
Drawings
The foregoing and other objects, features and advantages of the utility model will be apparent from the following more particular descriptions of exemplary embodiments of the utility model as illustrated in the accompanying drawings wherein like reference numbers generally represent like parts throughout the exemplary embodiments of the utility model.
FIG. 1 shows a schematic perspective view of an attitude angle adjustable aeroengine test stand according to one embodiment of the present utility model;
FIG. 2 shows a schematic top view of an attitude angle adjustable aero-engine test stand according to one embodiment of the present utility model;
FIG. 3 illustrates a schematic view of a first telescoping assembly of an attitude angle adjustable aircraft engine test stand according to one embodiment of the utility model;
FIG. 4 illustrates a schematic structural view of a second telescoping assembly of an attitude angle adjustable aircraft engine test stand according to one embodiment of the utility model;
fig. 5 shows a schematic structural view of a third telescopic assembly of an attitude angle adjustable aeroengine test stand according to an embodiment of the present utility model.
Reference numerals illustrate:
1. a mounting plate; 2. a connecting rod; 3. a single hole hinge; 4. a third telescoping assembly; 5. a double-hole hinge; 6. a cushion block; 7. the auxiliary hinged support; 8. a first telescoping assembly; 9. a second telescoping assembly; a second shock absorber; 11. a hanging ring loose-joint bolt; 12, hinging a support; 13. hoisting the threaded hole; 14. a second left-handed pull rod; 15. a second sleeve; 16. a second right-handed pull rod; 17. a second lock nut; 18. a first left-handed pull rod; 19. a first sleeve; 20. a first lock nut; 21. a first right-handed pull rod; 22. a first shock absorber; 23. a third left-handed pull rod; 24. a third sleeve; a third right-handed pull rod; 26. and a third lock nut.
Detailed Description
Preferred embodiments of the present utility model will be described in more detail below. While the preferred embodiments of the present utility model are described below, it should be understood that the present utility model may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the utility model to those skilled in the art.
As shown in fig. 1 and 2, the present utility model provides an attitude angle adjustable aeroengine test stand, comprising:
a mounting plate 1;
the two support frames are symmetrically arranged on the mounting plate 1, and the tops of the two support frames are respectively used for rotationally connecting with main mounting knots at two sides of the aero-engine;
at least one first telescopic component 8, first telescopic component 8 sets up between two support frames, and the one end of first telescopic component 8 articulates on mounting panel 1, and the other end of first telescopic component 8 is used for rotating with the pair of aircraft engine tail spout top to be connected.
Specifically, in order to solve the problems that the structure of a traditional test bench is relatively fixed, the attack angle, the attitude angle and the like of an engine cannot be adjusted, the change of the attack angle and the attitude angle in the flight process of an unmanned aerial vehicle cannot be simulated, and the experimental requirements of the aeroengine cannot be met, the utility model provides an attitude angle adjustable aeroengine test bench, the tops of two support frames of the test bench are respectively used for being rotationally connected with main installation joints on two sides of the aeroengine, one end of a first telescopic component 8 is hinged on a mounting plate 1, the other end of the first telescopic component 8 is used for being rotationally connected with auxiliary installation joints above a tail nozzle of the aeroengine, when the attack angle or the attitude angle of the aeroengine needs to be regulated, the aeroengine is enabled to rotate by taking the main installation joints as circle centers, the inclination angle of the aeroengine is changed, and the state of the engine in the flight process of the unmanned aerial engine is simulated, so that the experimental requirements are met.
Preferably, the support frame includes connecting rod 2 and second flexible subassembly 9, and the one end of connecting rod 2 is kept away from each other and all articulates on mounting panel 1 with the one end of second flexible subassembly 9, and the other end of connecting rod 2 is articulated with the other end of second flexible subassembly 9 each other and is connected.
Specifically, the installation of aeroengines with different installation sizes of various specifications can be adapted by replacing the connecting rods 2 with different lengths and adjusting the lengths of the second telescopic assembly 9 and the first telescopic assembly 8.
Preferably, the other end of the connecting rod 2 is provided with a circular hole, inside which the second damper 10 is mounted, and a center hole of the second damper 10 is used for inserting a corresponding main mounting knot.
Specifically, by designing the second damper 10 in the circular hole, the vibration of the aeroengine itself can be reduced, and the aeroengine can be protected.
As shown in fig. 3, the first telescopic assembly 8 preferably comprises:
the inner sides of two ends of the first sleeve 19 are respectively provided with a first left-handed internal thread and a first right-handed internal thread;
the first left-handed pull rod 18 and the first right-handed pull rod 21, the first left-handed pull rod 18 penetrates through one end of the first sleeve 19 and is in threaded connection with the first left-handed internal thread, and the first right-handed pull rod 21 penetrates through the other end of the first sleeve 19 and is in threaded connection with the first right-handed internal thread.
Specifically, when the length of the first telescopic component 8 needs to be adjusted, as the inner sides of the two ends of the first sleeve 19 are respectively provided with the first left-handed internal thread and the first right-handed internal thread, when the first left-handed pull rod 18 and the first right-handed pull rod 21 are respectively hinged on the auxiliary installation knot above the tail nozzle of the aeroengine and the mounting plate 1, the length of the first telescopic component 8 can be changed, the main installation knots on the two sides of the aeroengine can rotate in the two second shock absorbers, and the main installation knots are used as circle centers to tilt, so that the attack angle or the attitude angle of the aeroengine can be changed.
Preferably, the first telescopic assembly 8 further comprises two first lock nuts 20 screwed on the first left-hand tie rod 18 and two first lock nuts 20 screwed on the first right-hand tie rod 21.
Specifically, when the two first lock nuts 20 on the first left-handed pull rod 18 and the two first lock nuts 20 on the first right-handed pull rod 21 respectively lean against the two ends of the first sleeve 19, the first left-handed pull rod 18 and the first right-handed pull rod 21 can be restricted from moving and the first sleeve 19 can be restricted from rotating, and further, the stability of the first telescopic assembly 8 can be ensured.
As shown in fig. 4, the second telescopic assembly 9 preferably comprises:
the inner sides of two ends of the second sleeve 15 are respectively provided with a second left-handed internal thread and a second right-handed internal thread;
the second left-handed pull rod 14 and the second right-handed pull rod 16, the second left-handed pull rod 14 runs through one end of the second sleeve 15 and is in threaded connection with the second left-handed internal thread, and the second right-handed pull rod 16 runs through the other end of the second sleeve 15 and is in threaded connection with the second right-handed internal thread.
Specifically, when the length of the second telescopic component 9 needs to be adjusted, as the inner sides of the two ends of the second sleeve 15 are respectively provided with the second left-handed internal thread and the second right-handed internal thread, when the second left-handed pull rod 14 and the second right-handed pull rod 16 are respectively hinged to the other end of the connecting rod 2 and the mounting plate 1, the second sleeve 15 is rotated, the length of the second telescopic component 9 can be changed, and then the connecting rod 2 with different lengths can be replaced so as to adapt to the installation of aeroengines with different installation sizes of various specifications.
Preferably, the second telescopic assembly 9 further comprises two second lock nuts 17 screwed on the second left-hand tie rod 14 and two second lock nuts 17 screwed on the second right-hand tie rod 16.
Specifically, when the two second lock nuts 17 on the second left-handed pull rod 14 and the two second lock nuts 17 on the second right-handed pull rod 16 respectively lean against the two ends of the second sleeve 15, the second left-handed pull rod 18 and the second right-handed pull rod 16 can be restricted from moving and the second sleeve 15 can be restricted from rotating, and then, in a natural state, the stability of the second telescopic assembly 9 can be ensured.
Preferably, the test bench further comprises a double-hole hinge piece 5 and two third telescopic components 4, wherein the double-hole hinge piece 5 is arranged between the two supporting frames, one ends of the two third telescopic components 4 are hinged on the double-hole hinge piece 5, and the other ends of the two third telescopic components 4 are respectively hinged on the side walls of the two connecting rods 2.
Specifically, through adjusting the length of the third telescopic component, two second shock absorbers 10 can be appropriately far away from each other or be close to each other, and when the main installation knot at two sides of the aeroengine inserts two second shock absorbers 10, the main installation knot at two sides of the two second shock absorbers 10 can be guaranteed to be better fixed, and the main installation knot at two sides is prevented from falling off.
Preferably, a plurality of hoisting threaded holes 13 are arranged on the connecting rod 2, the hoisting threaded holes 13 are internally connected with the hoisting ring loose-joint bolts 11 in a threaded manner, and the other end of the third telescopic assembly 4 is rotatably connected to the hoisting ring loose-joint bolts 11.
As shown in fig. 5, the third telescopic assembly 4 preferably comprises:
the inner sides of the two ends of the third sleeve 24 are respectively provided with a third left-handed internal thread and a third right-handed internal thread;
the third left-handed pull rod 23 and the third right-handed pull rod 25, the third left-handed pull rod 23 runs through one end of the third sleeve 24 and is in threaded connection with the third left-handed internal thread, and the third right-handed pull rod 25 runs through the other end of the third sleeve 24 and is in threaded connection with the third right-handed internal thread.
Specifically, when the length of the third telescopic assembly 4 needs to be adjusted, since the inner sides of the two ends of the third sleeve 24 are respectively provided with the third left-handed internal thread and the third right-handed internal thread, when the third left-handed pull rod 23 and the third right-handed pull rod 25 are respectively hinged on the side walls of the double-hole hinge 5 and the connecting rod 2, the third sleeve 24 is rotated, the length of the third telescopic assembly 4 can be changed, and the two second shock absorbers 10 can be properly separated from or approaching to each other.
Preferably, the third telescopic assembly 4 further comprises two third lock nuts 26 screwed on the third left-hand tie rod 23 and two third lock nuts 26 screwed on the third right-hand tie rod 25.
Specifically, when the two third lock nuts 26 on the third left-handed pull rod 23 and the two third lock nuts 26 on the third right-handed pull rod 25 respectively lean against the two ends of the third sleeve 24, the movement of the third left-handed pull rod 23 and the third right-handed pull rod 25 and the rotation of the third sleeve 24 can be limited, and then, in a natural state, the stability of the third telescopic assembly 4 can be ensured.
Preferably, the support frame further comprises a single-hole hinge 3 and a main hinge support 12, the single-hole hinge 3 and the main hinge support 12 are far away from each other and are fixedly connected to the mounting plate 1, one end of the connecting rod 2 and one end of the second telescopic assembly 9 are hinged to the single-hole hinge 3 and the hinge support 12 respectively, and the center line of a hinge hole of the single-hole hinge 3 is perpendicular to the center line of a hinge hole of the hinge support 12.
Specifically, the center line of the hinge hole of the single-hole hinge member 3 is perpendicular to the center line of the hinge hole of the hinge support 12, so that the connecting rod 2 and the second telescopic assembly 9 can be prevented from tilting.
Preferably, the test bench further comprises at least one cushion block 6 and at least one auxiliary hinged support 7, wherein the cushion block 6 is arranged between the two supporting frames, the auxiliary hinged support 7 is fixedly connected to the cushion block 6, a first shock absorber 22 is installed at one end of the first telescopic component 8, and the first shock absorber 22 is hinged to the auxiliary hinged support 7.
Specifically, the first damper 22 may reduce vibration of the aircraft engine itself, thereby protecting the aircraft engine.
Preferably, the number of the first telescopic assemblies 8 is two, and the other ends of the two first telescopic assemblies 8 are used for rotationally connecting with the two pairs of mounting knots.
In particular, two first telescopic assemblies 8 are provided for improving the stability when adjusting an aeroengine.
Preferably, after the test bed is integrally installed, the mounting plate 1, the connecting rod 2 and the second telescopic assembly 9 are triangular, and the mounting plate 1, the connecting rod 2 and the third telescopic assembly 4 are triangular.
Specifically, the triangle shape has better stability, and simple structure, and the dismantlement and the installation of aeroengine of being convenient for.
In summary, when the attitude angle adjustable aeroengine test stand provided by the utility model is implemented, the aeroengine is placed on the attitude angle adjustable aeroengine test stand through a lifting appliance or a tool, the main mounting knots at two sides of the aeroengine respectively penetrate through the center holes of the two second shock absorbers 10, the auxiliary mounting knots above the tail nozzle of the aeroengine are connected through the first telescopic component 8 and are provided with the revolute pair, as one end of the first telescopic component 8 is provided with the first shock absorber 22, the first shock absorber 22 is hinged on the auxiliary hinged support 7, and further, through the cooperation of the second shock absorber 8 and the first shock absorber 22, the rigid impact between the aeroengine and the test stand can be reduced when the aeroengine is started;
when the attack angle or the attitude angle of the aeroengine needs to be adjusted, the first locking nut 20 is loosened, as the inner sides of the two ends of the first sleeve 19 are respectively provided with the first left-handed internal thread and the first right-handed internal thread, when the first left-handed pull rod 18 and the first right-handed pull rod 21 are respectively hinged on the auxiliary installation knot above the tail nozzle of the aeroengine and the mounting plate 1, the length of the first telescopic assembly 8 can be changed, the main installation knots on the two sides of the aeroengine can rotate in the two second shock absorbers 10, and the main installation knots are used as circle centers to tilt, so that the attack angle or the attitude angle of the aeroengine can be changed.
The foregoing description of embodiments of the utility model has been presented for purposes of illustration and description, and is not intended to be exhaustive or limited to the embodiments disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the various embodiments described.
Claims (9)
1. Aeroengine test bench with adjustable attitude angle, characterized in that, this test bench includes:
a mounting plate;
the two support frames are symmetrically arranged on the mounting plate, and the tops of the two support frames are respectively used for rotationally connecting with main mounting knots at two sides of the aero-engine;
the telescopic device comprises at least one first telescopic component, wherein the first telescopic component is arranged between two supporting frames, a first shock absorber is installed at one end of the first telescopic component, the first shock absorber is hinged to the mounting plate, and the other end of the first telescopic component is used for being rotationally connected with a secondary mounting structure above a tail nozzle of an aeroengine.
2. The attitude angle adjustable aeroengine test bed according to claim 1, wherein the support frame comprises a connecting rod and a second telescopic assembly, one end of the connecting rod and one end of the second telescopic assembly are far away from each other and are hinged on the mounting plate, and the other end of the connecting rod and the other end of the second telescopic assembly are hinged with each other.
3. The attitude angle adjustable aeroengine test bed according to claim 2, wherein a circular hole is formed in the other end of the connecting rod, a second shock absorber is mounted in the circular hole, and a center hole of the second shock absorber is used for inserting the corresponding main mounting knot.
4. The attitude angle adjustable aircraft engine test bench of claim 1, wherein the first telescoping assembly comprises:
the inner sides of two ends of the first sleeve are respectively provided with a first left-handed internal thread and a first right-handed internal thread;
the left-handed draw bar penetrates through one end of the first sleeve and is in threaded connection with the first left-handed internal thread, and the right-handed draw bar penetrates through the other end of the first sleeve and is in threaded connection with the first right-handed internal thread.
5. The attitude angle adjustable aircraft engine test bench of claim 2, wherein said second telescoping assembly comprises:
the inner sides of two ends of the second sleeve are respectively provided with a second left-handed internal thread and a second right-handed internal thread;
the second left-handed pull rod penetrates through one end of the second sleeve and is in threaded connection with the second left-handed internal thread, and the second right-handed pull rod penetrates through the other end of the second sleeve and is in threaded connection with the second right-handed internal thread.
6. The attitude angle adjustable aeroengine test bed according to claim 2, further comprising a double-hole hinge member and two third telescopic members, wherein the double-hole hinge member is arranged between the two supporting frames, one ends of the two third telescopic members are hinged on the double-hole hinge member, and the other ends of the two third telescopic members are respectively hinged on the side walls of the two connecting rods.
7. The attitude angle adjustable aircraft engine test bench of claim 6, wherein said third telescoping assembly comprises:
the inner sides of two ends of the third sleeve are respectively provided with a third left-handed internal thread and a third right-handed internal thread;
the third left-handed pull rod penetrates through one end of the third sleeve and is in threaded connection with the third left-handed internal thread, and the third right-handed pull rod penetrates through the other end of the third sleeve and is in threaded connection with the third right-handed internal thread.
8. The attitude angle adjustable aeroengine test stand according to claim 2, wherein the support frame further comprises a single-hole hinge member and a main hinge support, the single-hole hinge member and the hinge support are far away from each other and are fixedly connected to the mounting plate, one end of the connecting rod and one end of the second telescopic assembly are hinged to the single-hole hinge member and the hinge support respectively, and a hinge hole center line of the single-hole hinge member is perpendicular to a hinge hole center line of the hinge support.
9. The attitude angle adjustable aeroengine test stand according to claim 1, wherein the number of the first telescopic assemblies is two, and the other ends of the two first telescopic assemblies are used for rotationally connecting with the two auxiliary mounting knots.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223532220.8U CN219714752U (en) | 2022-12-29 | 2022-12-29 | Aeroengine test bench with adjustable attitude angle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223532220.8U CN219714752U (en) | 2022-12-29 | 2022-12-29 | Aeroengine test bench with adjustable attitude angle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN219714752U true CN219714752U (en) | 2023-09-19 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202223532220.8U Active CN219714752U (en) | 2022-12-29 | 2022-12-29 | Aeroengine test bench with adjustable attitude angle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN219714752U (en) |
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2022
- 2022-12-29 CN CN202223532220.8U patent/CN219714752U/en active Active
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